Show that the values vA and vP of the speed of an earth satellite at the apogee A and perigee P of an elliptic orbit are defined by the relations where M is the mass of the earth, and rA and rP represent, respectively, the maximum and minimum distances of the orbit to the center of the earth.

Transcribed Image Text:

A 2GM p 1₁ +1'p l'A 1/3 2GM TA TA + 1p 1p